Equilibrator for flying-machines.



E. D. STEVENSON.

EQUILIBRATOR FOR FLYING MACHINES.

APPLICATION FILED AN.15, 1913" Patented Oct. 14, 1913.

Wiinesses Cir shaft.

EDWIN D. STEVENSON, E VJADSWORTH, OHIO.

EQUILIBR-ATOR FORv FLYIlTG-MACHINES.

zlpplication filed January 15, 1918.

' following is a specification. s invention relates to equihbrators for it? mg; machines, its object being to provide 1 c ns ndcr the control of the motor of the ins; L no for exerting a constant upward upon said machine, said pullingmeans being connected to the machine at a point above the center thereof so that, when the machine tilts out of normal position, the pull exerted by the lifting device will tend to restore the equilibrium of the machine.

With the foregoing and other objects in vie'a which will appear as the description p oceeds, the invention resides in the combination and arrangement of parts and in the details of construction hereinafter described. and claimed, it being understood that changes in the precise embodiment of the invention herein disclosed, can be made within thescepe of what is claimed, without departingfrom the spirit of the invention. in the accompanying drai'vings the preferred forms of the invention have been shown.

in. said drawingsigrure 1 is a VlQW showing, diagrammatically, a flying machine in front elevation, said machine being tilted and the equilibrator being positioned to restore the late al balance of the machine. E2 is an enlarged side elevation of the equilibrator and showing one way of transmitting motion thereto from the propeller 3 is an enlarged section on line A-B 2. Fig. e is a vertical longitudinal section through a modified structure.

Referring to the .ligurcs by charzwters of reference C designates a portion of an aeroplane structure the same being provided 3 with a propeller shaft D adapted to be actuated by a motor E. Extending upwardly from the center of the machine and per dicular to the sustaining pla e or plancs is the supporting struciurc of the equilibrator, this structure being indicated at l and being rigidly mounted relative to the frame of the aeroplane.

in the .form of device shown in Figs. 1, 2 and 3, a frame 2 is mounted upon the upper end of the structure. This frame 2 supports gimbal made up of an. outer member 3 Specification of Letters Patent.

Patented @ct. 14k, 1%13.

Serial No. 742,290.

which can be in the form of a rectangular frame and an inner member 4 which can likewise be in the form of a rectangular frame. The member 3 -has trunnions 5 jour aled within the frame 2 or within arms (5 extending upwardly from the frame. The member is mounted on a shaft section 7 which extends through the member 3 at right angles to the axis of the. trunnions 5. Shaft section 7 has a gear 8 secured'thereto which meshes with another gear 9 secured to an upwardly extending shaft 10, this last named shaft being provided, its upper end, with a helicopter or elevating Wheel 11. A rod 12 extends downwardly from the middle portion of the member 4- and is provided the structure 1 and has a pulley or the like for receiving motion, through a belt 21, from a pulley 22 on the shaft D. @bviously chain and sprocket may be used in lieu of the belt and pulley or any other desired mechanism may be employed for transmit ting motion from shaft l) to shaft section'lS.

By mounting the pendulum in the mannor described, it will be seen that the same is free to sir inn in any direction. 1 Thus it will be seen that should the aeroplane tilt laterally or dip forwardly or backwardly, the pendulum will always remain vertical and the wheel ll will always be maintained substantially horizontal. its, when the machine tilts out of horizontal position, the gimbal will be shifted away from the Vertical center of the machine, as shown in Fig. .i, it will be seen that the upward force exerted by the rapidly rotating wheel 11 will tend automatically to restore the equilil rium of the machine no matter in What direction said machine may tilt. 3

Under some conditions it might be desirable to provide a helicopter which will only be capable of shifting in a plane extending transversely of the machine. Under these conditions, the same will be mounted as shown in Fig. 4 wherein the supporting structure ha been indicated at 23, this structure corresponding to the structure 1. A frame 24; is mounted within the said structure and is adapted to swing about a another gear 27 secured to the shaft 28 of the helicopter. A weighted rod 29 similar to the rod 12 is extended downwardly from frame 24:. With this construction it will be seen that whenever the machine tilts laterally, the rotating helicopter Wlll exert an upward pull thereon and tend to restore the lateral balance of the machine: It is to be understood that this helicopter wheel is always rotating While the propeller is in operation and, consequently, is always exerting an upward pull upon the machine so that the restoration of the lateral balance is effected automatically whenever the machine tilts' out of normal position.

It is to be understood that the herein described isnot in any sense to be considered a means for lifting the flying machine. The machine is intended to soar in the same manner as ordinary heavier than air machines and the helicopter herein described is merely designed as an attachment which can'be readily applied to ordinary machines and which merely exerts a lifting force in the manner described for the purpose of restoring the balance of the machine or for maintaining such balance.

"What is claimed is 1. The combination with an aeroplane, of a pendulum controlledhelicopter supported above the center of said aeroplane and adapted to swing relative thereto, said helicopter being normally positioned to 1'0- helicopter tate in a horizontal plane, and means for rotating the helicopter in any position in which it may be supported relative to the aeroplane structure. p

2. The combination with an aeroplane, of an equilibrator including a helicopter sup ported above the center thereof at a point fixed with relation to the frame of the aeroplane, weighted means for holding the helicopter normally in a horizontal plane of movement, and means for rotating the helicopter while the machine is in flight.

3. An'equilibrator f'or aeroplanes including an upwardly extending shaft mounted for'movement about a point fixed relative to the frame of the aeroplane-and above the center of said frame, weighted means .for holding said shaft normally vertical, a lifting wheel revoluble with the shaft, and means for rotating the shaft and wheel while the aeroplane is in flight.

4. The combination with an aeroplane, of an equilibrator including a structure fixedly mounted on the frame of the aeroplane and extending upwardly from,the center there of, a shaft mounted to swing relative to the upper portion of said structure, weighted means for holding the shaft normally vertical, an elevating wheel revoluble with the shaft, and means for rotatin the shaft and wheel while the aeroplane is being propelled shaft relative to the aeroplane frame.

In testimony that I claimthe foregoing as my own, I have hereto affixed my signature in the presence of two witnesses. EDWIN D. STEVENSON.

Witnesses M. C. LY'rLn, KATE P. LYTLE.

forward and independent of the angle of the 

